CN101155727A - Reduction of frictional losses in the region of boundary layers on surfaces, around which a fluid flows - Google Patents
Reduction of frictional losses in the region of boundary layers on surfaces, around which a fluid flows Download PDFInfo
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- CN101155727A CN101155727A CNA2006800115013A CN200680011501A CN101155727A CN 101155727 A CN101155727 A CN 101155727A CN A2006800115013 A CNA2006800115013 A CN A2006800115013A CN 200680011501 A CN200680011501 A CN 200680011501A CN 101155727 A CN101155727 A CN 101155727A
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- 239000000463 material Substances 0.000 claims description 46
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- 239000004744 fabric Substances 0.000 claims description 4
- 238000004080 punching Methods 0.000 claims description 2
- 230000001105 regulatory effect Effects 0.000 claims 1
- 238000005086 pumping Methods 0.000 abstract 1
- 238000009826 distribution Methods 0.000 description 10
- 239000011159 matrix material Substances 0.000 description 7
- 230000000694 effects Effects 0.000 description 4
- 229910052751 metal Inorganic materials 0.000 description 3
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- 229910000838 Al alloy Inorganic materials 0.000 description 2
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
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- 238000000576 coating method Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
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- 150000002739 metals Chemical class 0.000 description 1
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- 239000000758 substrate Substances 0.000 description 1
- 239000010936 titanium Substances 0.000 description 1
- 229910052719 titanium Inorganic materials 0.000 description 1
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F15—FLUID-PRESSURE ACTUATORS; HYDRAULICS OR PNEUMATICS IN GENERAL
- F15D—FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS
- F15D1/00—Influencing flow of fluids
- F15D1/10—Influencing flow of fluids around bodies of solid material
- F15D1/12—Influencing flow of fluids around bodies of solid material by influencing the boundary layer
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
- B64C21/06—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like for sucking
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C2230/00—Boundary layer controls
- B64C2230/04—Boundary layer controls by actively generating fluid flow
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C2230/00—Boundary layer controls
- B64C2230/22—Boundary layer controls by using a surface having multiple apertures of relatively small openings other than slots
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
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- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Physics & Mathematics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Jet Pumps And Other Pumps (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Laminated Bodies (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to an aerodynamic body having a plurality of throttle nozzles for limiting the fluid flow removed by pumping of the throttle nozzles (1) in an automatic adjusting mode. The invention also relates to an aerocraft arranged with the pump system. The invention also relates to the application of the throttle nozzles (1) to reduce the friction loss on the surface (8) on which the fluid flows on. The aerodynamic body of the invention comprises a plurality of throttle nozzles (1) of a throttle part (5) which is limited by an inlet (2) and an outlet (3), wherein, the inner wall of the throttle part is realized by the following way: when the pressure difference between the inlet (2) and the outlet (3) of the throttle part (5), turbulent flow is generated on the inner wall of the throttle part (5), thereby the effective flow section Aw is reduced in a self-adjusting way.
Description
The reference of related application
The U.S. Provisional Patent Application No.60/670 that the application requires to submit on April 11st, 2005 German patent application No.10 submitted on April 11st, 2,005 016570.2 and 2005,200 preceence, above-mentioned two disclosed contents of application are hereby incorporated by.
Technical field
Present invention relates in general to be used for reducing the implementation of fluid flows around lip-deep boundary layer region loss due to friction.The present invention be more particularly directed to aerodynamic body, it has a plurality of nozzles, is used in self-regulating mode the fluid stream of removing by nozzle suction being carried out throttling.The invention still further relates to the aircraft that disposes this suction system.At last, the present invention relates to the use of a plurality of above-mentioned throttle nozzles to reduce fluid flows around lip-deep loss due to friction.
In content of the present invention, the term aerodynamic body is meant the parts of aircraft in essence, described parts since air around their flow former thereby bear power-lift application force and aloft suction force respectively.This aerodynamic body especially comprises the aerodynamic body in the aerodynamic body group, and it comprises fuselage, wing, elevating rudder device, yaw rudder device and cowling.
Background technology
When fluid centers on a surface flow, in lip-deep boundary layer region, can produce loss due to friction usually at fluid flows.Understand appreciable impact relevant resistance to flow and loss due to friction by fluid in the respective type (laminar-type or Turbulent Flow Type) of the formed boundary 1ayer that flows on the hard substrate surface: during when the cambium layer laminar boundary layer, fluid flows around matrix surface on can be directly the lower relative velocity of generation, wherein, as shown in Figure 1a, the friction force that is produced is also lower.But, turbulent boundary layer be formed on fluid flows around matrix surface on directly cause higher relative velocity, wherein, these relative velocities are roughly corresponding to the speed of fluid on the matrix surface outside the described boundary 1ayer, thereby produce as the corresponding high friction force of diagram demonstration among Fig. 1 c.
Such loss due to friction is that people are undesirable naturally, in aviation and space technology field, people attempt by boundary 1ayer being stabilized in the laminar flow scope and with aircraft surface particularly the loss due to friction on the wing keep low as far as possible.For example, according to a kind of method at this problem, the suction mode that schematically shows by Fig. 1 b and remove suitable volume fluid stream from boundary 1ayer with planar fashion remains on boundary 1ayer in the laminar flow scope always.In this case, depend on the pressure in the flow direction and the distribution of lift by the fluid volume removed of suction.This fluid flow can produce by suction, this for example for fluid flows around matrix provide micro-perforated surface to realize, thereby the suction chamber that schematically shows by means of Fig. 2, be arranged in the micro-perforated surface below is removed suitable rate of volume flow by suction.
But, realize boundary 1ayer is stabilized in the scope of laminar flow by the suction current that produces certain volume and have multiple shortcoming.For example, suction power is adapted in time and become and/or be impossible, perhaps the quantity of suction chamber and/or the corresponding control of suction system needed irrational expenditure with the pressure condition that the position in flow direction becomes.Therefore, profit can make the volume of air of removing not enough or excessive the suction that boundary 1ayer is stabilized in the laminar flow scope by means of the suction current of micro-perforated surface generation certain volume in a known manner.
In addition, also can produce the variation of pressure and lift conditions transverse to flow direction.But known manner up to now is to produce certain volume suction fluid and boundary 1ayer is stabilized in the laminar flow scope still restive these variations of this mode by the rigidity suction chamber of extending transverse to flow direction.These pressure that in Fig. 3, shown in flow direction and in transverse to flow direction, produced and the variation of lift conditions with way of illustration, therefore can remove non-optimum air volume or air excess volume by suction inevitably, system and installation cost have so just unnecessarily been increased, for example increase corresponding controlling cost, caused extra unfavorable weight and production and running cost so again.
Summary of the invention
According to above-mentioned problem relevant with known way and shortcoming, purpose of the present invention is stabilized in mode in the laminar flow scope for a kind of being used for is provided with boundary 1ayer.Described known mode is by by means of micro-perforated surface be in suction chamber below the micro-perforated surface and produce the suction current of certain volume and boundary 1ayer is stabilized in the laminar flow scope.The present invention removes and boundary 1ayer is stabilized in the laminar flow scope by the suction of the proper volume flow on the aerodynamic body that fluid flows is centered on, wherein, mode of the present invention is best and automatically the rate of volume flow of being removed is adjusted to pressure and the lift distribution that fluid flows changes with position and time continuously on matrix.
This purpose can be by specially designed aerodynamic body, corresponding configuration aircraft and utilize a plurality of above-mentioned throttle nozzles to realize.
Aerodynamic body according to the present invention is included in its lip-deep a plurality of nozzles, and described a plurality of nozzles are used in self-regulating mode aspirating by described nozzle and the fluid stream of removing being carried out throttling.These nozzles comprise the restriction that is limited by entrance and exit respectively.Being constructed inside into of restriction makes effective flow cross section of nozzle reduce in self-regulating mode, makes the suction differential pressure between the entrance and exit of restriction simultaneously owing to forms turbulent former thereby increase on the inwall of restriction.
Therefore, basic conception of the present invention comprises: utilize the fluid flow state that produces on the aerodynamic body surface to combine with throttle nozzle with relevant pressure state, that is to say, utilize the following fact: promptly minimum suction force or pressure always act on (with the suction of negative sign mark) on the aerodynamic body surface location that produces peak flow rate (PFR).When the suction force that is limited of bearing in high-flow area when the outlet of this throttle nozzle is lower than (not being to be lower than very much) and acts on described lip-deep suction force, cambium layer flow volume fluid stream in the restriction of nozzle then.On the contrary, at other lower region generating of flow velocity higher suction force or pressure (with the suction of negative sign mark).In this case, the suction force of nozzle exit significantly is lower than the lip-deep suction force of aerodynamic body, and makes that the pressure drop on the restriction is higher, and produces turbulent flow in restriction.
Effective nozzle diameter of nozzle or obstruction free flow area are reduced to and produce turbulent flow on the inwalls of restriction, pass the accessible mobile of nozzle thereby weaken fluid.Increase along with pressure differential between the entrance and exit of restriction raises although pass the flow velocity of the fluid stream that nozzle removes by suction, comparatively speaking, the more remarkable effect of the turbulent flow that is produced, thus reduced to pass the fluid volume of restriction.
As mentioned above, very little differential pressure or suction force are fallen and can be caused approximate Laminar Flow therein between the restriction entrance and exit, and make flow section roughly corresponding to the free area of restriction.But,, then in restriction, produce tangible disturbed flow condition and the obstruction free flow area of restriction reduced if between the entrance and exit of restriction, produce significant differential pressure.So just may make throttle nozzle according to the present invention in high-flow area, remove the fluid stream of larger volume by suction, and therefore make turbulent boundary layer produce high loss due to friction, and the fluid by suction removal small size flows in low flow velocity zone, and therefore makes laminar boundary layer produce low loss due to friction.Therefore, the rate of volume flow of being removed by suction can be adjusted to suction required respectively on the boundary 1ayer under the different serviceability with position and time variation.
Therefore, so just no longer need to supply different spray nozzles structure, just as begin described known way at this paper, promptly boundary 1ayer is stabilized in the laminar flow scope by the suction fluid stream that on micro-perforated surface, produces certain volume with different-diameter.On the contrary, the single-nozzle structure with custom-designed inwall can be removed the optimal volume flow by suction all the time under any lift conditions.The mode that boundary 1ayer is stabilized in the laminar flow scope is compared by the suction fluid that produces certain volume with beginning is described, also no longer need to provide a plurality of suction chamber to guarantee the suction fluid of optimum volume consistently.Can guarantee all the time lip-deep optimal volume flow to be removed by the suction of each throttle nozzle according to throttle nozzle of the present invention, described throttle nozzle only has and is arranged in the single chamber of fluid flows around the aerodynamic body lower face.
Described restriction realizes to guarantee producing required turbulent flow on the restriction of nozzle with the form in labyrinth.This structure relates to any structure that produces the inwall of required turbulent flow on restriction.
The inwall of restriction can be the form of sharp edge serrations, and for example cutting or punching press are in the nozzle wall material.What also can expect is: other shapes that selection can cause turbulent flow to produce replace the form of described sharp edge serrations to realize the inwall of restriction.For example, can make the cross section of described inwall have arc convex, described arc convex can make and pass its fluid that flows generation turbulent flow.The inwall of restriction also can be designed by multiple other modes that those skilled in the art considers naturally according to application corresponding.
According to a specific embodiment, the cross section of above-mentioned serrations has spill continuous, that repeat (recessed waveform), thereby produces corresponding turbulent flow in the recess that forms like this.
As mentioned above, but the serrations cutting in the material of nozzle wall.So just can serrations be arranged to spiral fashion along the inwall of restriction.
As mentioned above, but the restriction cutting in being arranged in the first material layer fwd nozzle wall.If restriction and this first material layer extend in parallel and not exclusively pass this first material layer, cloth second material layer is covered in the both sides of first material layer, and described second material layer is furnished with corresponding opening or hole respectively to form the entrance and exit of restriction.These second material layers can be made extremely thinly and be made by for example aluminum alloy, and described second material layer is as the coating of first material layer, and one of them second material layer forms the surface of aerodynamic body.Comparatively speaking, first material layer that comprises described restriction can be by making such as any materials of metal, plastics etc.
Be to realize very desirable suction power, the thickness of first material layer should be roughly corresponding to the aperture in opening in second material layer or hole.Certainly, these indications are representative guiding suggestion roughly only, and it need be applicable to the particular case of respective application by those skilled in the art respectively.
In the above-described embodiments, described restriction extends in the plane of described first material layer and penetrates first material layer fully, makes the both sides of the material layer of winning need cover cloth second material layer to form restriction.But, if restriction incomplete penetration first material layer but for example near cutting vertically in first material layer, i.e. cutting then can be eliminated and cover the cloth expense in aerodynamic body.
Because custom-designed nozzle placement is on the aerodynamic body surface, it is enough to provide the aerodynamic body that only has single suction chamber, and described single suction chamber makes the outlet of a plurality of throttle nozzles stand to aspirate fluid.This single suction chamber for example can directly be arranged in the aerodynamic body lower face and bear the negative pressure of the appointment that is produced by suitable pump.In this case, the decisive factor of the suction force of suction chamber is the minimum local pressure of fluid flows in the matrix boundary 1ayer, only needs in this position by suction the rate of volume flow of appointment to be removed.On the contrary, in the implementation of initial described generation volume suction fluid, to make other positions (pressure of described other positions surpasses local minimal pressure) bear stronger suction and can not produce other favourable boundary 1ayer effects usually.Utilize the present invention, can design suction system more purposive and can design forr a short time, this be because the self-regulation flow velocity can prevent from by suction the excess volume flow to be removed.If distribution of pressure changes in flight course, for example changing on the wing and/or on elevating rudder and rudder unit, then this suction system can bring particularly advantageous effect.
According to another aspect of the present invention, utilize aircraft to realize basic purpose of the present invention, the shell of aircraft is realized with the form of aerodynamic body with above-mentioned feature at least in part.Certainly, bearing the form that all parts that change pressure distributes all can have an aerodynamic body of above-mentioned feature on the aircraft awing realizes.For example, comprise that at least one aerodynamic body in the aerodynamic body group of fuselage, wing, elevating rudder device, yaw rudder device and cowling can be at least in part realizes with the form of above-mentioned aerodynamic body.
According to another aspect of the present invention, realize basic purpose of the present invention by in the surface of aerodynamic body or in the shell of aircraft, using a plurality of throttle nozzles with above-mentioned feature, with the suction of a plurality of throttle nozzles by having single suction chamber and remove by the self-regulating rate of volume flow of throttle nozzle from described surface, thereby the boundary 1ayer of fluid flows around lip-deep fluid stream is stabilized in the laminar flow scope, reduces loss due to friction on described surface or the shell with this.
Therefore, the present invention's self-regulation that can provide required suction force according to the pressure that changes with position and time respectively and lift conditions.Because eliminated the needs that a plurality of suction chamber are provided according to corresponding line pressure state like this, the mode that the simple structure of suction system of the present invention also can be easier to realize realizes, thereby reduces weight to a certain extent and reduce equipment cost.Above-mentioned weight reduces and also can reduce by the used requirement that material satisfied.Owing to no longer need to have the nozzle of the micro-perforated surface of being made by titanium, the weight of utilizing the present invention to realize reduces and nozzle placement can be had in more highdensity first material layer (for example being made by different metals or plastics) aforesaid.
Description of drawings
Below with reference to accompanying drawing the present invention is explained in more detail.In the accompanying drawings:
Fig. 1 a has shown that fluid flows distributes around lip-deep laminar velocity;
Fig. 1 b has shown that fluid flows distributes around the stable laminar velocity of lip-deep suction;
Fig. 1 c has shown that fluid flows distributes around lip-deep turbulent velocity;
Fig. 2 has shown the cross-sectional plane of the wing with conventional suction system, and described conventional suction system is a feature with micropore and a plurality of suction chamber;
Fig. 3 has shown the projection of wing cross-sectional plane and described wing upward pressure and lift distribution;
Fig. 4 a has schematically shown the flow regime of throttle nozzle under low pressure reduction according to aerodynamic body of the present invention;
Fig. 4 b has schematically shown the flow regime of throttle nozzle under High Pressure Difference according to aerodynamic body of the present invention; And
Fig. 5 has shown preferred designs of nozzles.
In whole accompanying drawings, same or similar parts adopt identical reference marker to identify.Accompanying drawing just schematically shows and fict size.
The specific embodiment
For understanding the present invention better, 1a-1c and 2 describe background of the present invention and known suction system with reference to the accompanying drawings at first with reference to the accompanying drawings below.Accompanying drawing 1a-1c has shown three kinds of different velocity distribution that produce under different flow regimes.For example, Fig. 1 a has shown that the optimal flow with laminar boundary layer distributes.According to this figure, flow velocity drops to from the maxim outside the boundary 1ayer and carries out the transition to approaching zero the value of fluid flows around wing 8.As shown in the figure, if described speed drops to the value that is close to zero carrying out the transition to wing 8 places, this just means and only produces low loss due to friction.
On the contrary, Fig. 1 c has shown the velocity distribution of the turbulent flow above wing 8.Also drop in this case near zero value although carry out the transition to the speed at wing 8 places, this decline only occurs in the position of very close wing 8, thereby at the significant loss due to friction of the region generating of boundary 1ayer 4.
For addressing this problem, shown in Fig. 1 b, people often attempt removing suitable rate of volume flow by the suction by means of micropore 9 with planar fashion, thereby boundary 1ayer is stabilized in the laminar flow scope.
Shown such conventional suction system among Fig. 2.People can determine that wing 8 comprises the part with micro-perforated surface, and described micro-perforated surface contains a plurality of micropores 9.But the defective of this suction system is need to arrange a plurality of suction chamber 11 to remove the proper volume flow that flows around wing 8, wherein each independently suction chamber depend on the main lift conditions that Fig. 3 is shown.No matter described a plurality of required suction chamber 11 how, the diameter of described micropore 9 need change to utilize conventional suction system shown in Figure 2 to realize best effect.
But the fluid flows of wing 8 for example shown in Figure 3 not only changes on the flow direction of wing 8 around the lift distribution on the matrix, and changes on the extending range of the wing shown in the bottom view of Fig. 38.Distribution on this space also changes naturally in time, therefore, utilizes conventional suction system shown in Figure 2 almost can not control.
Below with reference to other accompanying drawings the present invention is described in more detail.4a, 4b with reference to the accompanying drawings, throttle nozzle 1 extends through the surface of wing 8.This nozzle comprises restriction 5, and this restriction 5 substantially vertically extends through inlet 2 and exports first material layer 6 between 3.In this case, this restriction 5 is characterised in that its inwall is to realize with the form of sharp edge serrations 4.This serrations 4 for example with the spiral form cutting in first material layer 6, thereby produce three-dimensional thread.But also can expect: 4 of serrations are passed first material layer 6 in the plane of as shown in Figure 5 first material layer 6, in this case, and the recess positioned opposite of the sawtooth of a side and opposite side.
Under the situation shown in Fig. 4 a, lift P
aWith suction force P
iBetween pressure reduction lower.In lift distribution shown in Figure 3, this situation roughly occurs in the position that lift is applied in maxim.Lift P
aWith suction force P
iBetween lower pressure reduction cause the laminar flow rate of volume flow of removing by throttle nozzle 1 suction.In this case, the obstruction free flow area A of throttle nozzle 1
wRoughly, make relatively large fluid flow cross suction and remove corresponding to the free area of restriction 5.But, the needed just result of this strong removal, this be because in the maximum lift region generating the highest flow velocity, dangerous maximum at this region generating turbulent boundary layer.
Under the situation shown in Fig. 4 b, lift P
aWith suction force P
iBetween pressure reduction be significantly higher than the situation shown in Fig. 4 a.In lift distribution shown in Figure 3, this situation roughly occurs in the low-down position of lift.Lift P
aWith suction force P
iBetween higher pressure reduction in the recess of serrations 4, produce turbulent flow, make the obstruction free flow area A of restriction 5
wReduce and remove less fluid stream by suction.But, in having the zone of low lift-to-drag ratios, satisfying this removal of passing through the minimizing of suction generation, this is the laminar boundary layer of formation certain degree because flow velocity is always lower in these positions.Therefore, under different serviceability, the total flow of removing by suction is adjusted to the suction requirement of boundary 1ayer ground best in similar self-regulating mode.
With reference to Fig. 5, throttle nozzle 1 comprise three material layers 6,7,7 ', wherein, outermost layer 7 ' form simultaneously surface according to wing 8 of the present invention.Restriction 5 is with the 6 substantially parallel extensions of first material layer and pass completely through first material layer 6.Described outer 7 ' comprise the appropriate well of the inlet 2 that forms restriction 5, and should skin 7 ' can make by the material as thin as a wafer of for example aluminum alloy.Internal layer 7 can be made similarly, and is feature with the hole of the outlet 3 that forms throttle nozzle.The layer of making by any materials of for example metal or plastics 6 described two layers 7,7 ' between and comprise the restriction 5 of form cutting in this layer with as shown in the figure sharp edge serrations.The thickness of described first material layer 6 roughly corresponding to the second layer 7,7 ' the aperture and should not surpass 0.5mm.
Except that shown in restriction 5, first material layer 6 also can be made into by this layer and carry the hot air that is used to heat aircraft skin in specific auxiliary air channel.Be alternatively: also can expect with form being that the heat with electric resistance lead pads existing this layer.The advantage of this embodiment is: can reduce by this way or even prevent to form from the teeth outwards ice.
Reference numerals list
1 throttle nozzle
2 entrances
3 outlets
4 sawtooth sections
5 restriction
6 first material layers
7,7 ' the second material layers
8 wings
9 micropores
10 aircraft fuselages
11 suction chamber
Claims (15)
1. aerodynamic body comprises:
The surface that-fluid flows centers on;
-a plurality of nozzles (1) in described surface, described nozzle is configured to carry out throttling in self-regulating mode to aspirating the fluid stream of being removed by nozzle (1);
Wherein said nozzle (1) is a feature with the restriction (5) that is limited by inlet (2) and outlet (3), and
The inwall of wherein said restriction (5) is realized in the following manner, promptly when the inlet (2) of restriction (5) and the pressure reduction increase between the outlet (3), owing to produce turbulent flow, obstruction free flow area (A on the inwall of restriction (5)
w) reduce in self-regulating mode.
2. aerodynamic body as claimed in claim 1, wherein said restriction (5) is embodied as the form in labyrinth.
3. aerodynamic body as claimed in claim 1 or 2, the inwall of wherein said restriction (5) is embodied as the form of sharp edge serrations (4).
4. that aerodynamic body as claimed in claim 3, the cross-sectional plane of wherein said serrations (4) have is continuous, repeat recessed waveform.
5. as claim 3 or 4 described aerodynamic bodies, wherein said serrations (4) is extended with spiral form along the inwall of described restriction (5).
6. as the described aerodynamic body of one of claim 1 to 5, (5) cutting of wherein said restriction or punching press are in first material layer (6).
7. aerodynamic body as claimed in claim 6, wherein said restriction (5) are basically parallel to described first material layer (6) and extend.
8. aerodynamic body as claimed in claim 7, wherein said restriction (5) passes completely through described first material layer (6).
9. as the described aerodynamic body of one of claim 6 to 8, cloth second material layer (7 is covered in the both sides of wherein said first material layer (6), 7 '), described second material layer (7,7 ') is furnished with inlet (2) and the outlet (3) of opening to form described restriction (5) respectively.
10. aerodynamic body as claimed in claim 9, the thickness of wherein said first material layer (6) are roughly corresponding to the bore dia of described second material layer (7,7 ') split shed.
11. hanging down basically, aerodynamic body as claimed in claim 6, wherein said restriction (5) extend as for described first material layer (6).
12. as the described aerodynamic body of one of claim 1 to 11, wherein said aerodynamic body comprises that the outlet that makes described a plurality of throttle nozzle (1) bears the single suction chamber of suction current.
13. an aircraft, the shell of described aircraft to small part adopt the form as aerodynamic body as described in one of claim 1 to 12 to realize.
14. aircraft as claimed in claim 13, wherein at least one aerodynamic body of the aircraft in the aerodynamic body group of being made up of wing, fuselage, elevating rudder device, yaw rudder device and cowling adopts the form as the described aerodynamic body of one of claim 1 to 12 to realize at least in part.
15. have application as a plurality of throttle nozzles (1) of feature as described in one of claim 1 to 12, be used to reduce the loss due to friction of fluid flows on surface (8), wherein, remove the rate of volume flow of the described fluid by throttle nozzle (1) in self-regulation mode regulated from described surface (8) by suction by described a plurality of throttle nozzles (1) by means of single suction chamber (11), thereby the boundary 1ayer of the fluid stream on the surface (8) that fluid flows is centered on is stabilized in the laminar flow scope.
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US60/670,200 | 2005-04-11 | ||
| DE102005016570.2 | 2005-04-11 | ||
| DE102005016570A DE102005016570A1 (en) | 2005-04-11 | 2005-04-11 | Fluid flow body e.g. wings, for airplane, has throttle nozzles comprising throttle section with inner wall that is designed, such that nozzle diameter/discharge cross-section is reduced due to turbulence formation in wall |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101155727A true CN101155727A (en) | 2008-04-02 |
| CN100586793C CN100586793C (en) | 2010-02-03 |
Family
ID=37055255
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200680011501A Expired - Fee Related CN100586793C (en) | 2005-04-11 | 2006-04-05 | Aerodynamic body |
Country Status (9)
| Country | Link |
|---|---|
| US (1) | US8091837B2 (en) |
| EP (1) | EP1868890B1 (en) |
| JP (1) | JP4876273B2 (en) |
| CN (1) | CN100586793C (en) |
| BR (1) | BRPI0608365A2 (en) |
| CA (1) | CA2597642C (en) |
| DE (2) | DE102005016570A1 (en) |
| RU (1) | RU2399555C2 (en) |
| WO (1) | WO2006108542A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102548841A (en) * | 2009-09-30 | 2012-07-04 | 空中客车德国运营有限责任公司 | Device for boundary layer suction and composite component therefor |
| CN109033645A (en) * | 2018-07-31 | 2018-12-18 | 中国人民解放军海军工程大学 | A kind of novel rudder for ship anticorrosion electrode and its design method |
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| US7924399B2 (en) | 2006-03-27 | 2011-04-12 | Asml Netherlands B.V. | Assembly comprising a conditioning system and at least one object, a conditioning system, a lithographic apparatus and methods |
| WO2011128069A1 (en) * | 2010-04-12 | 2011-10-20 | Airbus Operations Gmbh | Profile-plate portion for use as an outer wall of a flow body, method for producing a profile-plate portion, and flow-body component with a suction-extraction device for fluid |
| GB201114433D0 (en) * | 2011-08-22 | 2011-10-05 | Airbus Operations Ltd | Wing leading edge venting |
| US9746010B2 (en) * | 2014-04-09 | 2017-08-29 | University Of Florida Research Foundation, Incorporated | Noise control of cavity flows using active and/or passive receptive channels |
| US9758240B2 (en) * | 2014-04-25 | 2017-09-12 | Rohr, Inc. | Modular plenum and duct system for controlling boundary layer airflow |
| US10000277B2 (en) * | 2014-10-16 | 2018-06-19 | Rohr, Inc. | Perforated surface for suction-type laminar flow control |
| DE102015110782A1 (en) | 2015-07-03 | 2017-01-05 | Airbus Operations Gmbh | Integral component with an active flow control device |
| ES2688537T3 (en) * | 2016-01-12 | 2018-11-05 | Airbus Operations, S.L. | Edge of attack with laminar flow control and manufacturing procedure |
| US20170198988A1 (en) * | 2016-01-13 | 2017-07-13 | Hamilton Sundstrand Corporation | Vanes for heat exchangers |
| US10605280B2 (en) * | 2016-11-06 | 2020-03-31 | The Boeing Company | Phase tailoring for resonant flow devices |
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| GB2567683A (en) | 2017-10-20 | 2019-04-24 | Airbus Operations Ltd | Apparatus for laminar flow control |
| ES2943266T3 (en) | 2017-12-28 | 2023-06-12 | Airbus Operations Gmbh | Leading edge structure for an aircraft flow control system |
| US11433990B2 (en) | 2018-07-09 | 2022-09-06 | Rohr, Inc. | Active laminar flow control system with composite panel |
| RU2734664C1 (en) * | 2020-04-03 | 2020-10-21 | Федеральное Государственное Казенное Военное Образовательное Учреждение Высшего Образования "Тихоокеанское Высшее Военно-Морское Училище Имени С.О. Макарова" Министерства Обороны Российской Федерации (Г. Владивосток) | Perforated outer surface of rotation body with combined holes and suction channel |
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| US3203648A (en) * | 1961-12-26 | 1965-08-31 | Northrop Corp | Means for removing boundary layer air from aircraft |
| BE758739A (en) * | 1969-11-13 | 1971-04-16 | Fuji Photo Film Co Ltd | METHOD AND APPARATUS FOR TRANSPORTING A FLUID |
| US4671474A (en) * | 1984-06-21 | 1987-06-09 | The Boeing Company | Fluid control apparatus and method utilizing cellular array containing mini-vortex flow patterns |
| FR2583118A1 (en) | 1985-06-10 | 1986-12-12 | Irrifrance Sa Ste Nle | Energy-dissipating device with baffles and cavities having a swirling effect |
| US4932612A (en) * | 1986-02-25 | 1990-06-12 | Blackwelder Ron F | Method and apparatus for reducing turbulent skin friction |
| US5263667A (en) | 1991-09-09 | 1993-11-23 | The Boeing Company | Perforated wing panel with variable porosity |
| US5366177A (en) * | 1992-10-05 | 1994-11-22 | Rockwell International Corporation | Laminar flow control apparatus for aerodynamic surfaces |
| RU2032595C1 (en) | 1994-05-20 | 1995-04-10 | Акционерное общество закрытого типа "Лайт Маркет" | Device for regulating boundary layer |
| GB9914652D0 (en) * | 1999-06-24 | 1999-08-25 | British Aerospace | Laminar flow control system and suction panel for use therein |
-
2005
- 2005-04-11 DE DE102005016570A patent/DE102005016570A1/en not_active Ceased
-
2006
- 2006-04-05 DE DE602006007327T patent/DE602006007327D1/en active Active
- 2006-04-05 CN CN200680011501A patent/CN100586793C/en not_active Expired - Fee Related
- 2006-04-05 WO PCT/EP2006/003094 patent/WO2006108542A1/en active Application Filing
- 2006-04-05 BR BRPI0608365-0A patent/BRPI0608365A2/en not_active IP Right Cessation
- 2006-04-05 CA CA2597642A patent/CA2597642C/en not_active Expired - Fee Related
- 2006-04-05 US US11/911,138 patent/US8091837B2/en not_active Expired - Fee Related
- 2006-04-05 JP JP2008504680A patent/JP4876273B2/en not_active Expired - Fee Related
- 2006-04-05 RU RU2007139985/11A patent/RU2399555C2/en not_active IP Right Cessation
- 2006-04-05 EP EP06724042A patent/EP1868890B1/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102548841A (en) * | 2009-09-30 | 2012-07-04 | 空中客车德国运营有限责任公司 | Device for boundary layer suction and composite component therefor |
| US8800915B2 (en) | 2009-09-30 | 2014-08-12 | Airbus Operations Gmbh | Device for boundary layer suction and composite component therefor |
| CN109033645A (en) * | 2018-07-31 | 2018-12-18 | 中国人民解放军海军工程大学 | A kind of novel rudder for ship anticorrosion electrode and its design method |
| CN109033645B (en) * | 2018-07-31 | 2023-04-07 | 中国人民解放军海军工程大学 | Novel rudder anti-corrosion electrode and design method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CA2597642A1 (en) | 2006-10-19 |
| RU2399555C2 (en) | 2010-09-20 |
| BRPI0608365A2 (en) | 2009-12-29 |
| DE102005016570A1 (en) | 2006-10-19 |
| RU2007139985A (en) | 2009-05-20 |
| CN100586793C (en) | 2010-02-03 |
| EP1868890A1 (en) | 2007-12-26 |
| EP1868890B1 (en) | 2009-06-17 |
| CA2597642C (en) | 2012-12-18 |
| US20090266937A1 (en) | 2009-10-29 |
| JP4876273B2 (en) | 2012-02-15 |
| US8091837B2 (en) | 2012-01-10 |
| JP2008535720A (en) | 2008-09-04 |
| DE602006007327D1 (en) | 2009-07-30 |
| WO2006108542A1 (en) | 2006-10-19 |
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